Human Flying Saucer Patent Documents (1/2)

June 26, 1962 j. d. gibbs 3,041,012

AIRCRAFT

✓^2

INVENTOR.

Jesse PaJd&ffis

June 26, 1962

J- D. GIBBS

3,041,012

Filed March 21, 1961

AIRCRAFT

11 Sheets-Sheet 9

WM

Moll

INVENTOR.

3 , 041,012

Patented June 26, 1962

United States Patent Office

1

3,041,012

AIRCRAFT

Jesse David Gibbs, Box 351, Tuscarawas, Ohio
Filed Mar. 21, 1961, Ser. No. 97,375

2 Claims. (Cl. 244—17.23) 5

This invention relates to a flying machine or aircraft.

The primary object of this invention is to provide an
aircraft which is adapted to be conveniently used for
transporting cargo, passengers or the like, and wherein io
the aircraft of the present invention includes a novel
means for causing the aircraft to travel in the desired
location with the desired rate of speed.

A further object is to provide an aircraft of the type
stated which includes a highly efficient means for adjust- 15
ing the pitch of the propellers or blades whereby the
speed of the aircraft can be effectively regulated or con-
trolled as desired, and wherein there is also provided a
means for tilting or changing the angular position of the
propeller blades in order to provide a means for steering 20
or guiding the aircraft during flight.

A still further object of the present invention is to pro-
vide a flying saucer type of wingless aircraft which has
propellers arranged around a passenger or cargo com-
partment and wherein the aircraft can be made to fly in 25
a desired direction such as straight up, forward, back-
ward, or to each side, the aircraft being constructed so
that the propellers will distribute the lift in a balanced
and even manner so as to provide effective control of
the aircraft by the pilot thereof. 30

Still another object is to provide such an aircraft that is
economical to manufacture and efficient in operation and
which is rugged in structure and foolproof in use.

These and other objects of the invention will become
apparent from a reading of the following specification 35
and claims, together with the accompanying drawings,
wherein like parts are referred to and indicated by like
reference characters and wherein:

FIGURE 1 is a side elevational view of the aircraft
of the present invention. 40

FIGURE 2 is a sectional view taken on the line 2 — 2
of FIGURE 1.

FIGURE 3 is a sectional view taken on the line 3 3

of FIGURE 1.

FIGURE 4 is a fragmentary sectional view illustrating 45
certain constructional details of the present invention and
showing the various rings and the means for rotating the
propeller blades.

FIGURE 5 is a view generally similar to FIGURE 4
and showing the means for driving the upper propeller 50
rings in the desired direction.

FIGURE 6 is a diagrammatic view illustrating the up-
per and lower gear drive for rotating the propeller carry-
ing rings in opposite directions.

FIGURE 7 is a fragmentary sectional view showing a 65
portion of the mechanism for changing the pitch of the
propellers and also the means for elevating and lowering
the propeller carrying rings.

FIGURE 7 a is a fragmentary elevational view, with
parts broken away and in section showing the stationary 60
ring assembly and the means for raising and lowering the
propeller carrying rings.

FIGURE 7 d is a sectional view taken on the line
7b — 7b of FIGURE 7 a .

FIGURE 7° is an enlarged sectional view taken on the
line 7 C — 7° of FIGURE 7 a .

FIGURE 7 d is a sectional view taken on the lir
7 d — 7d of FIGURE 7 a .

FIGURE 7 e is a cross-sectional view taken through one
of the propeller blades.

FIGURE 8 is an enlarged sectional view showing a part
of the lowering and raising mechanism of FIGURE 7.

65

70

2

FIGURE 9 is an enlarged sectional view taken on the
line 9—9 of FIGURE 7.

FIGURE 10 is a fragmentary elevational view, with
parts broken away and in section, showing a portion of
the mechanism for changing the pitch of the propellers.

FIGURE 11 is a fragmentary top plan view showing a
portion of the mechanism of FIGURE 10.

FIGURE 12 is a fragmentary sectional view showing
the universal mounting for the propeller blades and the
rotating rings.

FIGURE 13 is a sectional view taken on the line 13 —

13 of FIGURE 12.

FIGURE 14 is a sectional view taken on the line 14 —

14 of FIGURE 2.

FIGURE 15 is a sectional view taken on the line
15— 15 of FIGURE 2.

FIGURE 16 is an enlarged sectional view showing a
portion of the mechanism of FIGURE 15.

FIGURE 17 is a fragmentary elevational view show-
ing the means for turning the pitch ring.

FIGURES 18 and 19 are fragmentary elevational views
showing the stop holes or openings in the pitch ring.

FIGURE 20 is a diagrammatic view showing a portion
of the housing of the aircraft and with one of the sta-
tionary rings mounted thereon and also showing the loca-
tion of the roller bearings for mounting one of the rotat-
ing rings.

FIGURES 21 and 22 are diagrammatic views showing
the position of the parts as for elevating straight ahead
or turning when the .aircraft is flying.

FIGURE 23 is a sectional view showing a slide bar for
keeping the rings from having side motion.

FIGURE 24 is a diagrammatic view showing the elec-
trical and mechanical means for controlling and changing
the pitch of the propellers as shown in FIGURE 24 a .

FIGURE 24 a is a diagrammatic view showing the
angle of pitch assumed by the propeller blades.

FIGURE 25 is a fragmentary sectional view illustrating
the cam mechanism as shown in FIGURE 24 for operat-
ing the contact rollers for making and breaking the cir-
cuits and also for operating the lock pin for the pitch
rings.

FIGURE 26 is a sectional view taken on the line 26 —

26 of FIGURE 25.

FIGURE 27 is a sectional view taken on the line 27 —

27 of FIGURE 25.

FIGURE 28 is a view similar to FIGURE 27 with the
cam in a different position.

FIGURE 29 is a view similar to FIGURE 26 with the
cam in a different position.

FIGURE 30 is an enlarged elevational view with parts
broken away showing the switch of FIGURE 24.

FIGURE 3 1 is a sectional view taken on the line 31 —

31 of FIGURE 30.

FIGURE 31 a is a sectional view taken on the line
31 a — 31 a of FIGURE 30.

FIGURE 32 is a sectional view taken on the line 32 —

32 of FIGURE 30.

FIGURE 33 is a sectional view taken on the line 33 —

33 of FIGURE 30.

FIGURE 34 is an enlarged sectional view showing a
part of the main body of the machine with the landing
legs mounted thereon and in retracted position.

FIGURE r>5 is a sectional view taken approximately
on the line 35—35 of FIGURE 34.

FIGURE 36 is a sectional view taken on the line 36—36
of FIGURE 34.

FIGURE 37 is sectional view taken through the peri-
scope used for viewing the ground from a cabin when
taking-off or landing.

FIGURE 38 is a sectional view taken approximately
on the line 38—38 of FIGURE 37.

8, (Ml, 012

3

FIGURE 39 is a sectional view taken on the line 39 — 39
of FIGURE 37.

Referring in detail to the drawings, the numeral SO in-
dicates the aircraft of the present invention which is
shown to comprise a hollow housing 51 that may be
shaped to include a cylindrical wall portion 49, and the
aircraft is provided with an upper dome 52 as well as a
lower depending section 53, FIGURE 1. The dome 52
may be made of a suitable transparent material such as
a suitable plastic, and the dome 52 may be provided with
reinforcing grips 54.

As shown in FIGURE 34, for example, there is pro-
vided within the housing 51 of the aircraft spaced parallel
horizontally disposed decks or platforms 55 and 56 which
define in the housing lower and upper compartments 57
and 58. The upper compartment 58 is adapted to receive
or support therein passengers, cargo or the like, and ar-
ranged in the lower compartment 57 is an engine or motor
59, FIGURE 3. The motor 59 serves to operate a shaft
60 which has a gear 61 thereon, and the gear 61 meshes
with a gear 62 on a shaft 63, and the shaft 63 is connected
to an electrical generator 64 which can be used for supply-
ing electricity for the various components of the aircraft.

Also arranged in the lower compartment 57 is a pair
of engines or motors 65 of a suitable construction, and the
motors 65 serve to operate the shafts 66 which have gears

67 thereon, FIGURE 3, and the gears 67 mesh with gears

68 on shafts 69. As shown in FIGURE 7 for example
there is provided upper and lower ring gears 70 which
surround the housing 51, and the upper and lower ring
gears 70 are provided with teeth 71 thereon, there being
gears 72 on the shafts 69 which mesh with the teeth 71
of the ring gears 70.

There is further provided upper and lower tubular sup-
port rings which surround the housing 51 and which are
secured thereto or formed integral therewith, and arranged
within the support rings 73 are tracks or rails 74, FIG-
URE 7. The numeral 75 designates each of a pair of
upper and lower ring members which are arranged for
rotation around the support rings 73, and the ring gears
70 are secured to or formed integral with the ring mem-
bers 75. Tapered bearings such as the bearings 76 are
adapted to be secured to the ring members 75 as for ex-
ample by means of securing elements 77, and the tapered
bearings 76 are mounted for movement through the tracks
74 in the support rings 73.

The numeral 78 indicates tubular hollow ring elements
that surround the housing 51, and the ring elements 78
are secured to or formed integral with the ring members
75. There is also provided pitch rings 79 which surround
the housing, and the pitch rings 79 have teeth 80 along
a portion thereof, FIGURE 2, and the numeral 81 indi-
cates a gear which meshes with the teeth 80 of the pitch
ring, the gear 81 being driven by a suitable electric motor
82. As shown in FIGURE 5 for example, lugs 83 are
affixed to each ring element 78 or secured thereto or
formed integral therewith, and pins 84 extend through the
lugs 83, and the pins 84 also extend through slots 85 in
the pitch rings 79.

Referring to FIGURES 10 and 11 of the drawings, it
will be seen that there is provided a gear reduction unit
which is indicated generally by the numeral 87, and the
gear reduction unit 87 includes a gear section 88 that
meshes with teeth 86 on an adjacent pitch ring 79, and
the gear reduction unit 87 includes a gear section 89
contiguous to the gear section 88, and these gear sec-
tions 88 and 89 are arranged on a supporting shaft 90.
The gear reduction unit 87 further includes a gear 91
which meshes with the gear 89, and the gear 91 is adapted
to be arranged on a shaft 92 along with a gear 93, and the
gear 93 meshes with a gear 94 that is affixed to or keyed
to a shaft 95. A shield or cover member 96 may be
provided for the gear reduction unit 87. The shaft 95 is
connected to a driven shaft 48 through the medium of a
universal joint 97, FIGURE 7, and the numeral 98 desig-

4

nates each of a plurality of propellers or blades. Each
of the propellers 98 is provided with a recess or opening
99 in an end thereof for receiving a corresponding shaft
48, and the propeller 98 is adapted to be secured to the
5 shaft 48 as for example by means of securing elements
100. As shown in FIGURE 7 e , the side edge portions of
the propeller 98 are tapered as at 101, and the propeller
is provided with an elongated enlarged shoulder or ridge
102. The propeller 98 also has a recess or opening 103
10 for receiving therein with a slidable connection, a shaft

104. The shafts 104 are connected to tubular ring pieces

105, and surrounding the ring pieces 105 are tubular ring
units 106, FIGURE 5. The ring units 106 are provided
with inner tracks or rails 107 whereby tapered bearings

15 such as the bearings 76 that are affixed to the ring piece
105, can travel through the tracks 107 so as to minimize
friction between these moving parts. The numeral 108
indicates universal joints for connecting the shafts 104
to the ring pieces 105.

20 The aircraft of the present invention further includes a
circular support unit which is indicated generally by the
numeral 109, and the support unit 109 consists of a plu-
rality of arcuate or curved sections 110 which have their
adjacent ends joined together by body elements 111 , and
25 as shown in the drawings each of the body elements 111
includes spaced apart arcuate wall members 112. The
wall members 112 are provided with slots and grooves 113
and 114, FIGURE 7 d , and there is provided a plurality
of sliding racks 115 which have tongues 116 mounted for
30 sliding movement in the grooves 114. Bars or arms 118
have pins 117 extending therethrough, and the pins 117
are mounted for sliding movement through the slots 113.
Motors 119 are provided for rotating gears. 120, FIGURE
7 b , and the gears 120 mesh with gears 121 on shafts 122.
35 The shafts 122 have gears 123 thereon that mesh with
gears 124 on shafts 125, and the shafts 125 have gears
126 thereon, and the gears 126 mesh with the teeth 127 of
the racks 115.

The arms 118 are connected to plate portions 128 of
40 the racks 115 by means of the pivot pins 117.

There is further provided connector assemblies which
are indicated generally by the numeral 129, and the con-
nector assemblies 129 include bracket members 130 that
have interfitting parts 131, FIGURE 7 a and FIGURE 9,
45 and the numeral 132 indicates a pin or stud which extends
through the interfitting parts 131, there being a bracket
133 secured to or formed integral with the stud 132,
Rollers 134 are movably mounted in the bracket 133,
and a rod 135 is connected to the rollers 134, there being
50 spaced apart collars 136 and 137 on the rod 135, FIG-
URE 7. The rod 125 extends through a bracket piece
139 that is secured to a corresponding ring 106, and a
coil spring 138 is arranged on each rod 135 as shown in
the drawings, for a purpose to be later described.

55 There is further provided a plurality of spaced apart
brace assemblies 140, FIGURE 3, and the brace assem-
blies 140 include outer hollow members 143 that are
pivotally connected as at 142 to ears 141, and the ears
141 are secured to or formed integral with the inner sur-
00 faces of the ring pieces as shown in the drawings. Inner
members 144 are mounted for telescoping or sliding move-
ment in the outer members 143, and the inner members
144 are pivotally connected between ears 145 as at 146,
and the ears 145 are secured in place as shown in FIG-
05 URE 3 for example.

As shown in the drawings upper and lower spaced
parallel circular plates 147 are secured to or formed
integral with the wall portion 49 of the housing 51, FIG-
URE 14, and a plurality of concentrically arranged tracks
70 148 are suitably affixed to the plates 147, and the tracks
148 are insulated from the plates as for example by means
of insulation 149, FIGURE 16. Electrical conductors or
wires ISO are electrically connected to the tracks 148.
The numeral 151 indicates a supporting bracket, and
75 arranged contiguous to the bracket 151 is a driving motor

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5

152 which serves to rotate or selectively drive a cam 154
that is mounted on a shaft 153, The cam 154 includes
a pair of sections 155 and 156, and the sections 155 and
156 are arranged in superposed relation with respect to
each other. The numeral 157 indicates a rod which has
a portion 153 arranged in engagement with the first cam
section 155, and the rod 157 includes a supporting sec-
tion 159 which has a plurality of rollers 160 rotatably
supported thereon, and the rollers 160 have contacts 162
and insulation 161 and 163 contiguous thereto, FIG-
URE 16.

As shown in FIGURE 24 for example there is fur-
ther provided locking pins 164 which have their inner
ends pointed as at 165 for selectively engaging openings
or holes 166 and 167 in the pitch rings 79, and spring
members 168 are operatively connected to the locking
pins 164 for normally urging or biasing the locking pins
164 inward towards the pitch rings 79. The locking pins
164 include outer end portions 169 that are arranged in
engagement with the second cam sections 156 of the
cams 154.

As shown in FIGURE 24, there is also provided a
locking rod 171 which is adapted to have its inner ends
selectively engage notches 170 on the pitch rings 79, and
a solenoid 172 is connected to the outer end of the rod
171, there being a coil spring 173 circumposed on an
outer end portion of the rod 171. A contact 174 is car-
ried by the rod 171, and the contact 174 is mounted for
movement into and out of electrical engagement with a
contact 175 so that as later described in this application
an electrical circuit can be selectively opened or closed
to the motor 82 in order to control shifting movement
of the pitch ring whereby the pitch of the propellers 98
can be varied or regulated as desired.

The electrical circuit for the aircraft of the present in-
vention farther includes switches 176 and 183, FIGURE
24. As shown in the drawings the switch 176 consists of
a circular disc 177 which has an arm or bar 178 pivotally
connected thereto as at 179, and terminals 180 on the
disc 177 are adapted to be selectively engaged by con-
tacts 182 on the end portions 181 of the arm 178.

The second switch 183 is shown to comprise a casing
184, FIGURE 31, and the casing 184 is recessed as at

185 so as to provide a generally circular wall surface

186 that has a flanged section 187 thereon, FIGURE 30, 45
and a plurality of spaced apart terminals 188 are connect-
ed to the flanged section 187. The numeral 189 indicates
conductor rings in the casing 184, and wires or conductors

190 are electrically connected to the rings 189. As shown

in FIGURE 31 for example a securing element or pin 50

191 extends through the central portion of the casing 184,
and a movable arm 192 includes a hub or knob portion
193 that is mounted on the pin 191, and the knob por-
tion 193 is adapted to be roughened or knurled as at 194

so as to facilitate the manual gripping and rotation there- 55
of. The numeral 195 indicates a pawl or dog which is
carried by the outer end of the arm 192, and the pawl
195 is urged outwardly by a spring member 196, the
pawl 195 being adapted to selectively engage notches 197
that are arranged in the section or surface 186 of the 60
casing 184. A contact 198 is carried by the arm 192 for
selectively engaging a terminal 199, and a contact 200
on the arm 192 is adapted to selectively engage a ter-
minal 261. The numeral 202 indicates a wire or con-
ductor which is electrically connected to the contact 198, 65
and the conductor 202 is adapted to extend through a
portion of the arm 192. The arm 192 is movably mount-
ed in a recessed portion 203 of the base 190. A contact
portion 204 on the base 190 is adapted to electrically
have an electrical conductor 205 connected thereto, and 70
a terminal 206 has a conductor 207 connected thereto.

In FIGURE 3 the numeral 208 indicates a passageway
which can be used for permitting passengers, cargo or the
like to be conveniently elevated into the passenger or
cargo compartment of the aircraft and a suitable elevat-

6

ing mechanism can be used in conjunction with the
passageway 208 to facilitate the ascending or descending
of the passengers, cargo or the like.

As shown in the drawings, the aircraft of the present
5 invention further includes a plurality of leg assemblies
which are each indicated generally toy the numeral 209,
and these leg assemblies each have the same construc-
tion. While the aircraft has been illustrated with three
of these leg assemblies 209, it is to be understood that
10 the number thereof can be varied as desired or required.
Each of the leg assemblies 209 includes an outer member
or bushing 218 that is secured to or formed integral with
the main housing of the aircraft, FIGURE 34, and a
sleeve 211 is slidable in the bushing 210. The bushing
15 210 is provided with a slot 222, and pins 212 are suitably
affixed to the sleeve 211, and the pins 212 are adapted
to project through the slot 222 in order to prevent rotation
of the sleeve 211. The numeral 213 indicates an ex-
ternally threaded screw member which is arranged in
20 threaded engagement with the sleeve 211, and the screw
member 213 includes a reduced diameter upper end por-
tion 214 which has guide members 215 arranged in en-
gagement therewith, FIGURES 34 and 35, and the guide
members 215 are connected to a block 216. A means is
25 provided for rotating the screw member 213 and this
means comprises a gear 217 which is suitably affixed
to the end portion 214, and the gear 217 has a worm
218 arranged in meshing engagement therewith, and a
shaft 219 is provided for rotating the worm or gear 218.
30 The shaft 219 may be turned or rotated by any suitable
means and as for example an engine, motor or the like
can be used for rotating the shaft 219, or else a hand
crank can be used for rotating the shaft 219.

As shown in the drawings, a spring member 220 is
35 connected to the lower end of each sleeve 211, and a
foot 221 is suitably affixed to each spring member 220.
The spring members 220 function as shock absorbers so
as to help cushion the landing impact of the aircraft.

In order to facilitate observation from the aircraft, as
40 for example during landing or take-off, there is provided
a periscope which is indicated generally by the numeral
223, FIGURE 1 and FIGURES 37, 38 and 39. The
periscope 223 embodies an outer member or element 224
which is rotatable in bearings 225, and a partition 226 in
the outer member 224 defines a chamber 227 through
which moves an endless chain 228. The chain 228 is
trained over sprockets 229 that are suitably affixed to
trunnions or stub shafts 230 and 231, and the periscope
further includes manualy movable knobs 232 which can
be used for simultaneously shifting the angular position
of upper and lower prisms 233 and 234. Viewing mem-
bers 235 and 236 are suitably affixed to the upper and
lower ends of the periscope as shown in the drawings.

As shown in FIGURE 3 for example, there is provided
a plurality of radially disposed braces 237 for helping to
maintain the housings 111 and their associated parts in
their proper aligned position.

The numeral 238 indicates gear trains which consist
cf intermeshing gears which provide a driving connection
between the shaft of the motor 152 and the cam 154.

From the foregoing, it is apparent that there has been
provided an aircraft of the flying saucer type which can
be used for various purposes such as military purposes or
else it can be used in connection with peaceful transporta-
tion or the like, and the aircraft of the present invention
can be used for transporting passengers, cargo or the like.

With the parts arranged as shown in the drawings, it
will be seen that the aircraft 50 of the present invention
includes the housing 51 which may have a cylindrical
formation, and the upper and lower sections 52 and 53
may be arranged as shown in FIGURE 1, and the inte-
rior of the housing may be divided into compartments
such as the compartments 57 and 58 by means of the
horizontally disposed deck or floors 55 and 56, and these
75 compartments can have engines, passengers or the like

3,041,012

conveniently arranged therein. The compartment 57 may
have the motors or engines 59 and €5 therein, and these
engines may be actuated by any suitable means as for
example by a suitable fuel such as gasoline, and the en-
gine 59 serves to drive the generator 64 through the inter-
meshing gears 61 and 62 and the generator 64 can be
used for supplying electrical energy for operating the var-
ious control mechanisms, lights or other accessories on
the aircraft.

The engine 65 serves to rotate the shafts 66 which have
the gears 67 thereon, and the gears 67 mesh with the
gears 68 on the shafts 69, the shafts 69 having the gears
72 thereon which mesh with the teeth 71 of the ring gears
70 so that actuating the pair of engines 65 the upper and
lower ring gears 70 can be caused to rotate around the
housing 51. In view of the fact that the ring gears 7®
are secured to or formed integral with the annular mem-
bers or rings 75, as for example as shown in FIGURES 4
and 5, it will be seen that this rotation of the ring gears
70 will rotate the rings 75, and the rings 75 carry the bear-
ings or rollers 76 which travel in the rails 74 so that the
rings 75 will be properly aligned as they rotate around
the rings 73. The rings 73 are fixedly secured to the wall
portion 49 of the housing 51, but as previously stated the
rings 75 are free to rotate around the rings 73. The rings
75 have secured thereto the rings 78, FIGURES 4 and 5,
and as the rings 75 turn they carry the rings 78 therewith.
The rings 78 are operatively connected to the propellers
98 through the medium of the shafting 48 so that this
rotation of the rings 78 will cause the upper and lower
sets or groups of propellers 98 to rotate and in view of
the fact that the upper set of the propellers 98 rotate in
an opposite direction from the lower set of propellers 98,
a counter balancing effect will be created or provided on
the housing 51 whereby the housing 51 will not rotate.
This rotation of the propellers 93 will provide lift or
thrust so that the aircraft can be ready to travel in a gen-
eral vertical upward or downward direction, or else as
later described in this application the aircraft can be made
to fly forward or backward or in a desired angular direc-
tion. The propellers 98 include an intermediate thickened
portion as shown in FIGURE 7 e , and the outer edges of
the propeller tapered to a sharp edge as indicated by the
numeral 101 so that a propeller of a highly efficient con-
struction is provided which will travel through the air in
such a manner as to provide the maximum amount of
thrust or lift in the most efficient manner.

The outer portion of the propellers 98 are slidably con-
nected to the shafts 104 by means of the openings or re-
cesses 103, and according to the present invention a
means is provided for varying the pitch of the propellers
98 so that by varying the pitch of the propellers the speed
of flight of the aircraft can be readily controlled or regu-
lated as desired.

In addition, a means is provided for tilting the propel-
lers 98, as for example the angle of the propellers can
be tilted from a position such as that shown in FIGURE 7
to a position shown in FIGURE 2 1 or the propellers can
be tilted back and forth from positions similar to those
shown in FIGURES 21 and 22 and this tilting of the pro-
pellers provides a means for steering the aircraft or caus-
ing the aircraft to travel in a desired direction or up and
down as desired.

To tilt the propellers 98, there is provided on the inter-
mediate non-rotating support unit 109, the slide bars or
arms 118 which are operatively connected to the rings
106, so that by moving the slide bars or arms 118 as for
example by actuating the motors 119, the rings 106 can
be raised or lowered in order to correspondingly raise or
lower the rings 105 which will have the effect of tilting
the propellers 98 to the desired location.

The aircraft of the present invention further includes
the extensible or retractable legs 209, and for example
when the aircraft is in flight the legs 209 can be moved
to a retracted position, and when the aircraft is landing

the leg assemblies 2®9 can be extended. To extend the
legs 209, it is only necessary to rotate the shaft 219 as
for example by means of a hand crank, motor or the like,
and this will rotate the gear 218 that meshes with the gear
5 217 so as to turn the screw member 213. Longitudinal
shifting of the screw member 213 is prevented by the
guides 215 which are connected to the block 216. As the
screw member 213 is rotated, it will cause the sleeve 211
to be moved up or down in view of the fact that the sleeve
10 211 is arranged in threaded engagement with the threaded
portion of the screw member 213, and the pins 212 ex-
tend from the sleeve 211 through the slot 222 in the bush-
ing 21® so as to prevent rotation of the sleeve 211. This
longitudinal shifting of the sleeve 211 will cause the spring
15 member 220 to move in a corresponding direction, and
since the spring 22® is connected to the foot 221, it will
be seen that the foot 221 will move with the sleeve 211.
The spring 22® functions as a shock absorber to help
cushion the landing impact of the aircraft.

20 There is also provided a periscope 223 which is adapt-
ed to be of a suitable construction so as to permit a pilot
or other person in the aircraft to more readily view the
area in the vicinity of the aircraft as for example when
the aircraft is landing or taking off, and for example a
25 pilot may look through the viewing member 235 and due
to the provision of the opposed prisms 233 and 234, the
area in the line of vision of the viewing member 236 can
be viewed by a person looking through the viewing mem-
ber 235. The prisms 233 and 234 are operatively con-
30 nected together for simultaneous adjustment as for exam-
ple by means of the chain 228 which is trained over
sprockets 229 so that by manually turning the knobs 232
the angular position of both prisms 233 and 234 can be
simultaneously adjusted in order to permit the user to set
35 the periscope in such a manner that a particular area can
be readily observed. The periscope is adapted to be con-
veniently supported in a bearing assembly 225 whereby
the periscope can be readily rotated in order to widen the
range of vision that is adapted to be covered by the
40 periscope.

The parts can be made of any suitable material and in
different shapes or sizes.

It is to be noted that the aircraft of the present inven-
tion is provided with upper and lower sets of propellers
45 93, and there is provided for each of the sets of pro-
pellers upper and lower pitch adjusting means as well
as upper and lower means for tilting the angle of the
propellers and since the construction of the upper and
lower assemblies are generally the same it is thought that
50 a description of one will suffice for both. However, the
upper propellers do rotate in an opposite direction from
the lower propellers so as to insure that the housing 51
will remain free of rotation because the oppositely ro-
tating propellers will counter balance any tendency to
55 cause rotation of the housing 51.

The means for raising and lowering or tilting the pro-
pellers is generally as follows. As shown in FIGURE
7 b there are two of the motors 119 for each housing 111,
and these motors 119 can l be energized individually or
60 collectively to either raise the top or bottom ring 106 in
order to tilt the upper or lower propeller mechanism, as
for example as shown in FIGURE 21 or FIGURE 22.
In actuating the propeller tilting mechanism as for ex-
ample to steer the aircraft, the switch 176 is first actuated
65 by moving the arm 178 to the position shown in FIGURE
24 and this will complete an electrical circuit to a motor
152 which will retract the locking pin 164 from the open-
ing 156 in which it is arranged, and the electrical circuit
can be completed to the switch 183 and this will energize
70 the solenoid 172 so that the rod 171 will be retracted from
the notches 170, and the contacts 175 and 174 will be
dosed in order to complete the circuit to the motor 82.
With the motor 82 energized, the gear 81 will be turned,
and since the gear 81 meshes with the teeth 80, it will he
75 seen that this actuation or energization of the motor 82

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9

will rotate the pitch ring 79. By rotating the pitch ring
79 or shifting the pitch ring 79, the teeth 86 of the pitch
ring will cause rotation of the gear 88 of the gear reduc-
tion unit 87 and this in turn will rotate the shaft 90
which in turn will cause rotation of the gear 89 that 5
meshes with the gear 91, and rotation of the gear 91 ro-
tates the shaft 92 which has the gear 93 thereon. The
gear 94 meshes with the gear 93, FIGURE 11, and the
gear 94 is on the shaft 95, so that the shaft 95 will be
shifted or turned, and since the shaft 95 is connected to io
the shaft 48 through the universal mounting 97, it will
be seen that this shifting of the pitch ring 79 will cause
the propellers 98 to be shifted or have their pitch changed
and the pitch of the propellers can be set or regulated as
desired or required in order to effectively and efficiently 15
control the speed of the aircraft. That is, by having the
propellers set at a particular pitch, the aircraft can be
made to fly or travel at a particular speed for a given
power output of the engines, and by varying or changing
the pitch of the propellers, the speed for a particular en- 20
gine output can be changed as desired.

The mechanism shown in FIGURES 7 a through 7 C for
example is adapted to he used for tilting the propellers
to different angles, and for example by properly energiz-
ing the motors 119, the shafts 122 can be rotated through 25
the provision of the intermeshing gears 120 and 121, and
this rotation of the shafts 122 will cause rotation of the
gears 126 as previously described, and since the gears 126
mesh with the teeth 127 of the racks 115, it will be seen
that the racks 115 will be shifted between the walls 112 30
of the housing 111. In view of the fact that the arms
or slide bars 118 are connected as at 117 to the moving
racks 115, it will be seen that this movement of the racks
115 by energization of the motors 119 will cause the
arms 118 to move the rings 106 towards or away from 35
the housing 111 due to the provision of the connector
mechanism 129 and its associated parts. That is, by
causing the arms 118 to move, the rings 106 can be
moved towards or away from the support 109 and since
the rings 106 are affixed to the rings 105, and in view 40
of the fact that the rings 105 are connected by means of
the universal joints 108 to the shafts 104, it will be seen
that the outer portions of the propellers can be raised or
lowered in order to position the propellers at a desired
angular position whereby this construction provides a 45
means of causing the aircraft to travel in a level flight,
move up or down or in any desired direction. The shafts
104 are slidably fitted in the openings 103 in the outer
portions of the propellers so that a sliding connection
is provided for the propellers in order to compensate for 50
different positions of the propellers so that there will be
no binding of the parts.

The braces 140 embody a telescoping connection so
that the braces 140 can help maintain the parts in their
proper aligned positions regardless of the shifted or tilted 55
position of the propellers.

The aircraft of the present invention embodies an elec-
trical system for operating or changing the pitch of the
propellers and also for raising and lowering the units to
change the angle of the propeller rings. There is also 60
provided a locking and unlocking mechanism in conjunc-
tion with the pitch changing arrangement. Suitable cali-
brated scales or instrument gauges or indicating mech-
anisms can he used in conjunction with the switches and
control mechanisms so that the parts can be set accurately 65
at the desired location or position.

The engines can be operated from any suitable source
of power such as gasoline, diesel fuel or the like.

It will therefore be seen that according to the present
invention there has been provided a wingless aircraft 70
that has propellers positioned around the passenger com-
partment instead of over, under, in front or behind the
compartment, and the aircraft of the present invention
will fly straight up, forward, back or to one side. There
is provided a mechanism consisting of a ring around the 75

10

outer tip of the propellers so as to distribute the lift to
the outer and inner tips in an even and uniform manner.
By having the upper and lower sets of propellers turning
in opposite directions with respect to each other, there
will be provided a means for stabilizing the passenger
compartment so that the passenger compartment or hous-
ing will not rotate. It is to be understood that various ac-
cessories are adapted to be used in conjunction with the
aircraft such as seats, an instrument panel, windows, a
parachute compartment, fuel tanks, luggage compart-
ments, and the like. The aircraft of the present inven-
tion utilizes oppositely spinning rotors or propellers to
insure that the aircraft can travel in the most efficient
manner, and there is also provided a means for tilting and
changing the pitch of the propellers so that the speed and
flight direction can be readily controlled.

Referring to FIGURE 24 of the drawings, it is to be
noted that when the switch 176 is in the position shown,
current goes to the motor 152, and the cam 156 first pulls
the pin 164 from the openings 166 and then the cam 165
shifts the rod 157 so as to move the rollers 160 into or
out of engagement with the proper rings 148 so as to
stop the motor 152. The switch 176 is then actuated
by moving its arm 178 from the solid line position of
FIGURE 24 to the dotted line position of FIGURE 24
so that an electrical current goes to the switch 183. By
turning the knob 193, the contacts close and the elec-
trical current goes to the motor 82 when the contacts 174
and 175 are closed. The propeller shifting ring is pro-
vided with the nine notches 170 to correspond with the
nine holes 166 and 167. As the switch 183 is moved,
current is first supplied to the solenoids 172 which re-
tracts die pin 171 from the notch 170 and then the motor
switch 183 is actuated, and the motor runs until the pin
171 drops in the next notch 170 and then the contacts
175 and 174 open so as to stop the motor 82 whereby
the propellers will have moved approximately ten degrees.
When the switch 183 is operated in the opposite direction,
the motor 82 is reversed.

The switch 183 is adapted to be operated by moving
its arm 192 until the dog 195 enters a notch 197, and the
motor runs until the pin 171 enters a notch 170 in the
pitch ring 179.

It is to be noted that according to the present invention
the motor 59 operates the shaft 60 and gears 61, and the
gear 61 meshes with the gear 62 on the shaft 63. The shaft
63 is connected to the electrical generator 64, and the
motor 59 supplies power for the electrical generator 64.
The electrical generator 64 is adapted to supply electricity
to all motors with the exception of the motors 59 and 65,
and also supplies electricity for all electrical accessories
or the like. The motor 59 is adapted to he a lightweight
air cooled engine which utilizes gasoline as its fuel, al-
though other types of fuel such as kerosene, diesel or the
like can be used. The electrical generator 64 is also
adapted to be made light in weight and air cooled.

The engines or motors 65 operate shafts 66 and gears
67, and the gears 67 meshes with the gear 68 on the shaft

69. The shaft 69 operates the gears 72, and the gears 72
mesh with the teeth 71 of the upper and lower ring gears

70. The upper and lower ring gears 70 which are secured
to or formed into the upper and lower ring members, are
arranged as shown in the drawings. The engines or mo-
tors 65 supply the power for rotating the propeller, and
the engines or motors 65 are preferably lightweight air
cooled aircraft engines which will pass requirements such
as FAA requirements, and the operating fuel may be gaso-
line, kerosene, diesel fuel or the like.

The support rings 73 are secured to or formed into the
housing 51. The tracks or rails 74 are secured to or
formed into the support rings 73. The upper and lower
ring members 75 which have upper and lower ring gears
70 secured to or formed integral therewith, are provided
as shown, and tapered bearings 76 are seemed to the ring
members 75 by means of securing elements 77, the ta-

3,041,013

11

pered bearings 76 being mounted for movement through
tracks in the support rings 73, and these tapered bearings
76 are adapted to be adjusted by the securing elements 77
which will locate the upper and lower ring members 75
away from the tracks 74 and support rings 73. The ring
members 75 will be held away evenly from the tracks 74
and the support rings 73.

The ring elements 78 are secured to or formed into the
ring members 75. The pitch rings 79 have teeth 80 along
a portion thereof, and gear 81 meshes with the teeth of
the pitch rings 79. The gear 81 is driven by an electric
motor 82. The lugs 83 are secured to or formed into
the ring elements 78, and pins 84 extend through the
lugs 83, and the pins 84 also extend through the slots 85
in the pitch ring 79. The lugs 83 and pins 84 hold the
pitch rings 79 and permit it to turn in either direction.
The electric motor 82 supplies power to turn pitch rings
79 in either direction. The electric motor 82 is adapted
to be a light weight air cooled reduction motor.

The gear reduction unit 87 includes a gear section 88
that meshes with the teeth 86 and adjacent pitch ring 79.
The gear reduction 87 includes a gear section 89 contigu-
ous to gear section 88, and these gear sections 88 and 89
are arranged on supporting shaft 90. The gear 91 meshes
with the gear 89, and the gear 91 is on the shaft 92 along
with the gear 93. The gear 93 meshes with the gear 94
on the shaft 95. The shield or cover member 96 is to
cover the gear reduction unit 87. The shaft 95 is con-
nected to a driven shaft 48 through the medium of a uni-
versal joint 97. Propellers or blades 98 have openings
99 in an end for receiving a corresponding shaft 48, and
propellers 93 are secured to the shaft 48 by means of
securing elements 180. The propellers 98 are tapered
on the edges 101, and have elongated enlarged shoulders
or ridges 102. These propellers 98 have recesses or open-
ings 103 for receiving a slidable connection or shaft 104.
The shafts 104 are connected to the ring pieces 105, and
ring units 106 surround the ring pieces 105. The tracks
or rails 107 are secured to or formed into the ring units
106. The tapered bearings 76 are secured to the ring
pieces 185 by means of securing elements 77, and the uni-
versal joints 108 are for connecting the shafts 104 to ring
pieces 105. The gear reduction unit 87 is for when gear
81 rotates one full turn, the propellers 98 will turn ten
degrees. The electric motor 82 turns the pitch rings
79, and in turn turns gear reduction unit 87, v/hich also
in turn turns propellers 98 through universal joints 97.
The tapered bearings 76, due to the provision of the se-
curing elements 77, and both ring members 75 and ring
pieces 105, permit the propellers 98 to rotate about the
housing 51. The universal joints 97 and 108 are to
permit the propellers 98 to change the angle as hereinafter
explained.

The circular support units 109 consist of curved sections
110 which have adjacent ends jointed together by body
elements 111. The body elements include spaced apart
wall members 112, and the wall members 112 have slots
or grooves 113 and 114. The sliding racks 115 have
tongues 116 for sliding movement in the grooves 114.
Pins 117 extend through bars or arms 118 and are mounted
for sliding movement through the slots 113. Motors 119
have the gears 120 connected thereto, and the gears 120
mesh with the gears 121 on the shaft 122, the shafts 122
having gears 123 that mesh with gears 124 on shafts 125.
The shafts 125 have gears 126 that mesh with the teeth
127 of the racks 115, and the electric motors 119 are
preferably light in weight and air cooled gear reduction
motors.

The arms 118 are connected to plate portions 128 of the
racks 115 by means of the pivot pins 117.

As shown in the drawings, the connector assemblies
129 include bracket members 130 that have interfitting
parts 131, and the interfitting parts 131 are connected to
the arms 118 by pins 118a. The pin or stud 132 extends
through the interfitting parts 131, and the bracket 133

1 9

is secured to or formed into with the stud 132. The rollers

134 are movably mounted in the bracket 133, and a rod

135 is connected to the rollers 134 with collars 136 and
137 spaced apart on rod 135. The rod 135 extends

5 through a bracket piece 139 that is secured to a correspond-
ing ring 106, and a coil spring 138 is arranged on each
rod 135.

The electric motors 119 drive racks 115 which have
arms 118 connected so that they may pivot. The arms
10 US are connected to the interfitting parts 131 so that
they too may pivot. The interfitting parts 131 are made
so that they can bend in the middle over the stud 132.
The interfitting parts 131 are connected to the bracket 133
by the stud 132. The bracket 133 has a slanted track
15 therein, by Which the rollers 134 roll. The rollers 134
are connected to the rod 135, and the rod 135 has collars

136 and 137 spaced on it, and spring 138 is connected
to the rod 135, and the bracket piece 139. When the
ring unit 186 changes angle, as at one point being raised

20 and at the other two points being lowered, the bracket
133 will turn to compensate for the change of position
of ring unit 106. The spring 138 is for the purpose to
return bracket 133 to the original position, when the
ring units 106 are level again. The interfitting parts 131
25 are for compensating arms 118 when they raise and
lower.

It is to be noted that the brace assemblies 140 include
outer hollow members 143 that are pivotally connected
as at 142 to ears 141, and the ears 141 are secured to or
30 formed into the ring pieces 105. The inner members
144 are mounted for telescoping or sliding movement in
the outer members 143, and the inner members 144 are
pivotally connected between the ears 145 as at 146, and
the ears 145 are secured to or formed into ring elements
35 78. Brace assemblies 149 are to help the propellers 98
so that they will not create a back lash at the ring pieces
105.

The circular plates 147 are secured to or formed into
wall portion 49 of the housing 51. The tracks 148 are
40 affixed to the plates 147. The tracks 148 are insulated
from the plates 147 by means of insulation 149. The
electrical conductors or wires 150 are electrically con-
nected to the tracks 148. The supporting bracket 151 is
contiguous to a driving motor 152 which serves to rotate
45 or selectively drive a cam 154 that is mounted on the
shaft 153. The cam 154 includes a pair of sections 155
and 156, and the sections 155 and 156 are arranged in
superimposed relation with respect to each other. The
rod 157 which has a portion 158 arranged to engage with
50 the first cam section 155, and the rod 157 includes a sup-
porting section 159 which has rollers 160 rotatably sup-
ported, the rollers 160 having contacts 162 and insulation
161 and 163 arranged adjacent thereto.

As shown in the drawings, locking pins 164 have their
55 inner ends pointed as at 165 for selectively engaging
openings or holes 166 and 167 in the pitch rings 79, and
spring members 168 are operatively connected to the
locking pins for normally urging or biasing the locking
pins 163 inward towards the pitch rings 79. The locking
60 pins 164 include outer end portions 169 that are arranged
in engagement with the second cam section 156 of the
cams 154.

The locking rod 171 which is adapted to have its inner
ends selectively engage the notches 170 in the pitch rings
65 79, is arranged as shown, and a solenoid 172 is connected
to the outer end of the rod 171. The coil spring 173 is
circumposed on an outer end portion of the rod 171, and
the contact 174 is carried by the rod 171, and the contact
174 is mounted for movement into and out of electrical
70 engagement with a contact 175.

The switch 176 consists of a circular disc 177 which
has an arm or bar 178 pivotally connected at 179, and
terminals 180 on the disc 177 are adapted to engage the
contacts 182 on the end portions 181 of the arm 178.

75 The switch 183 is recessed as at 185 to provide a cir-

3.04-1.012

13

cular wall surface 186 that has a flanged section 187.
Terminals 188 are connected to the flanged section 187.
Conductor rings 189 in the casing 184, and wires or con-
ductors 190 are electrically connected to the rings 189.
The securing element or pin 191 extends through the
center portion of the casing 184, and a movable arm 192
includes a hub or knob portion 193 that is mounted on
the pin 191, and the knob portion 192 is roughened or
knurled as at 194 so as to be readily gripped manually.
The pawl or dog 195 which is carried by the outer end of
the arm 192, is urged outwardly by the spring member
196, the pawl 195 is adapted to engage notches 107 that
are arranged in the section or surface 186 of the casing
184. The contact 198 is carried by the arm 192 for en-
gaging a terminal 199, and a contact 200 of the arm 192
engages a terminal 201. The wire or conductor 202
which is electrically connected to the contact 198, and
the conductor 202 extends through a portion of the arm
192. The arm 192 is movably mounted in the recessed
portion 203 of the base 190. The contact portion or
pulsating unit 204 on the base 190 with the electrical
conductor 205 connected, and a terminal 206 for a pul-
sating unit 204 has a conductor 187 connected thereto.

It will be noted that electricity will flow to the switch
176 to the three terminals one at terminal 181 and two
at terminal 180. As shown in locked position, as the
electricity flows to the terminal 181 through the contact
182 to the electrical tracks 148 and to the motors 152
which turn cams 154 that let the rod 164 lock in the pitch
rings 79 and the rod 157 can move the rollers 160 to the
opposite tracks breaking contact. Also in the position
shown electricity will not flow to the switch 183. Turn-
ing the arm 178 into the other position electricity flows
to the terminal 180 through the contact 182 to the elec-
trical tracks 148 and to the motor 152 which turn the
cams 154 to let the rod 164 unlock from pitch rings 79
and rod 157 will move the rollers 160 to the original
tracks. Also, the electricity will flow to the terminal 180
opposite the side through the contacts 182 to the switch
183, at the conductor ring 189 through the conductors
190 through the conductor 202 to contacts 198 and
200. The contacts 198 and 200 engage with the termi-
nals 199 and 201. The terminal 199 is for reversing and
terminal 201 is for forwarding motor 82. The pawl 195
is to hold the arm 192 in place in the notches 197. The
electricity from the terminals 199 and 201 also flows
through a solenoid 172 and back through the electrical
conductor 205 to the contact portion or pulsating unit
204, the solenoid 172 pulls the rod 171 out of notches
170 and the contacts 174 and 175 connect allowing the
motor 82 to operate. The contact portion or pulsating
unit 204 will pulsate so as to let the rod 171 into the next
notch 170. The terminal 206 contacts the terminal 188
and each time the terminal 206 contacts a terminal 188
the contact portion or pulsating unit 204 will pulsate the
same number of times. Conductor 207 is for electricity
to operate the pulsating unit 204.

The passageway 208 serves to permit passengers, cargo
or the like to move therethrough.

The leg assemblies 209 include the outer members
or bushings 210 that are secured to or formed into the
main housing, and the sleeve 211 is slidable in the bush-
ing 210. The bushing 210 has a slot 222, and pins 212
are affixed to the sleeve 211, and the pins 212 project
through the slot 222 to prevent rotation of the sleeve
211. Externally threaded screw members 213 are ar-
ranged in threaded engagement with the sleeve 211, and
the screw member 213 includes a reduced diameter upper
end portion 214 which has guide members 215 arranged
in engagement therewith. The guide members 215 are
connected to a block 216. Rotating screw member 213
is accomplished by the gear 217 affixed to the end por-
tion 214, and the gear 217 meshes with the worm 218.
The shaft 219 is powered by a motor or crank or the like.

The spring member 220 is connected to the lower end

14

of each sleeve 211, and a foot 221 is affixed to each
spring member 220 in order to cushion the landing of the
aircraft.

As shown in the drawings, the periscope 223 includes
5 an outer member or elements 224 which is rotatable in
bearings 225, and a partition 226 in the outer member
224 defines a chamber 227 through which moves an end-
less chain 228. The chain 228 is trained over sprockets
229 affixed to trunnions or stub shafts 230 and 231.
10 Knobs 232 are used for shifting the angular position of
the upper and lower prisms 233 and 234. The viewing
members 235 and 236 are affixed to the upper and lower
end of the periscope 223, and the periscope is for view-
ing the underside of the aircraft while landing or the
15 like.

Radially disposed braces 237 function as an added
support from the main housing to the circular support
unit for changing the angle of the propellers.

The gear train 238 between the motor 152 and the cam
20 154 serves as a reduction unit for the cam 154.

It is to be noted that the aircraft of the present inven-
tion embodies a tubular design which provides a light-
weight construction without loss of strength, and wherein
the material for making certain of the parts may be
25 aluminum, steel or the like and any suitable material can
be used that will pass FAA requirements.

Minor changes in shape, size and rearrangement of
details coming within the field of invention claimed may
be resorted to in actual practice, if desired.

30 What is claimed is:

1. In an aircraft, a housing, upper and lower sets of
propellers mounted for rotation about said housing,
means for varying the pitch of the propellers, and means
for tilting the angular position of the propellers, said

35 housing having a plurality of compartments therein, said
upper and lower sets of propellers rotating in opposite
directions relative to each other, a means for tilting the
propellers comprising a circular support surrounding said
housing and interposed between the upper and lower sets
40 of propellers, and power operated means on said sup-
port operatively connected to said propellers, extensible
legs depending from said aircraft, said legs having spring
supported feet associated therewith, a periscope depending
from the aircraft, said propellers including tapered edge
45 portions, and manually operable switch means for regulat-
ing and controlling the varying of the pitch of the
propellers.

2. An aircraft comprising a housing, engines in said
housing, shafts driven by said engines, gear means on

50 said shafts, upper and lower ring gears surrounding said
housing and said ring gears having teeth thereon mesh-
ing with said gear means, spaced parallel upper and lower
tubular support rings surrounding said housing and
secured thereto, rails in said support rings, rotary ring
55 members surrounding said support rings, bearings con-
nected to said ring members 'and said bearings being mov-
able in said rails, said ring gears being affixed to said
ring members, ring elements surrounding said housing and
said ring elements being affixed to said ring members,
Go pitch rings surrounding said housing and said pitch rings
having teeth on a portion thereof, a motor driven gear
member meshing with the teeth of a pitch ring; a plurality
of spaced apart lugs on each ring element, pins connected
to said lugs, there being spaced apart slots in said pitch
65 rings for the projection therethrough of said pins, said
pitch rings each having a toothed portion, a gear reduc-
tion unit connected to a ring element and said gear reduc-
tion unit including a gear element meshing with the
toothed portion of the pitch ring, a drive shaft connected
70 to said gear reduction unit, a driven shaft connected to
said drive shaft through the medium of a universal joint,
a propeller connected to said driven shaft, there being
recesses in the outer ends of the propellers, stub shafts
slidably engaging said recesses, a hollow tubular ring
75 piece connected to said stub shafts by means of universal

3,041,013

IS

joints, bearings connected to said ring piece, tubular ring
units surrounding said ring pieces, rails in said ring units
for receiving said last named bearings; a circular support
unit surrounding said housing and said support unit com-
prising a plurality of hollow arcuate sections having their 5
adjacent ends connected together by body elements, said
body elements each comprising wall members provided
with slots and grooves therein, toothed racks having
tongues slidable in the grooves in said wall members,
gears meshing with said toothed racks, motors for operat- 10
ing said last named gears, plates affixed to said racks,

IS

arms having end portions pivotally connected to said
plates, connector assemblies operatively connecting said
arms to said ring units, and support means for said pitch
rings, support unit, and motors.

References Cited in the file of this patent
UNITED STATES PATENTS

968,860 Kummer Aug. 30, 1910

1,868,392 Leffert July 19, 1932

2,444,332 Briggs June 29, 1948

2,740,595 Bakewell Apr. 3, 1956